RU2002110696A - GAS TURBINE ENGINE - Google Patents

GAS TURBINE ENGINE

Info

Publication number
RU2002110696A
RU2002110696A RU2002110696/06A RU2002110696A RU2002110696A RU 2002110696 A RU2002110696 A RU 2002110696A RU 2002110696/06 A RU2002110696/06 A RU 2002110696/06A RU 2002110696 A RU2002110696 A RU 2002110696A RU 2002110696 A RU2002110696 A RU 2002110696A
Authority
RU
Russia
Prior art keywords
gas turbine
turbine engine
bearings
compressor
combustion chamber
Prior art date
Application number
RU2002110696/06A
Other languages
Russian (ru)
Other versions
RU2225523C2 (en
Inventor
Виталий Владимирович Иванов
Валерий Алексеевич Кузнецов
Original Assignee
Открытое акционерное общество "Авиадвигатель"
Filing date
Publication date
Application filed by Открытое акционерное общество "Авиадвигатель" filed Critical Открытое акционерное общество "Авиадвигатель"
Priority to RU2002110696/06A priority Critical patent/RU2225523C2/en
Priority claimed from RU2002110696/06A external-priority patent/RU2225523C2/en
Publication of RU2002110696A publication Critical patent/RU2002110696A/en
Application granted granted Critical
Publication of RU2225523C2 publication Critical patent/RU2225523C2/en

Links

Claims (1)

Газотурбинный двигатель, включающий компрессор, камеру сгорания и турбину привода компрессора, консольный ротор которого установлен в переднем радиально-упорном и заднем радиальном подшипниках, опоры которых закреплены на внутреннем корпусе камеры сгорания, отличающийся тем, что между валами компрессора и турбины установлена резьбовая втулка, а отношение расстояния между подшипниками к величине осевых зазоров между статором и ротором в уплотнениях опоры радиального подшипника составляет 30-150.A gas turbine engine including a compressor, a combustion chamber and a compressor drive turbine, the cantilever rotor of which is mounted in the front angular contact and rear radial bearings, the bearings of which are mounted on the inner housing of the combustion chamber, characterized in that a threaded sleeve is installed between the compressor and turbine shafts, and the ratio of the distance between the bearings to the axial clearance between the stator and the rotor in the seals of the radial bearing support is 30-150.
RU2002110696/06A 2002-04-22 2002-04-22 Gas-turbine engine RU2225523C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2002110696/06A RU2225523C2 (en) 2002-04-22 2002-04-22 Gas-turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2002110696/06A RU2225523C2 (en) 2002-04-22 2002-04-22 Gas-turbine engine

Publications (2)

Publication Number Publication Date
RU2002110696A true RU2002110696A (en) 2003-11-20
RU2225523C2 RU2225523C2 (en) 2004-03-10

Family

ID=32390342

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2002110696/06A RU2225523C2 (en) 2002-04-22 2002-04-22 Gas-turbine engine

Country Status (1)

Country Link
RU (1) RU2225523C2 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2644660C1 (en) * 2017-03-07 2018-02-13 Акционерное общество "ОДК-Авиадвигатель" Gas turbine engine

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